Turbine



March 5, 1929. A. BONOM TURBINE Filed June 1'7. 192'." 4 sheets-sneer 2 A. BONOM March 5, 1929.

TURBINE 4 Sheets-.Sheet Filed June 17. 1927 Fig.q.

lavan/E01 Y aqf''anomj V744 Patented Mu. 5,1929..

UNITED STATES PATENToFFlcE.

ALFRED BONOM, 0F MONDOVI, ITALY.

, 'mamma Application le'd'J'une 17, 1927, Serial No. 199,595, and i'n Italy larok 22, 1927.

This invention relates to radial turbines with two rotors turning in opposite directions and has for its object an improved machine which is exceptionally compact owing to a rational arrangement of its parts, as well -as simple in construction and assembly and of a high thermic efficiency.

According to this invention the turbine generally comprises at leastptwo stages, a

i-gh-pressure and a low-pressure stage, respectivelyx, arranged concentrically so as to deliver t e pressure high-pressure stage to the low-pressure stage, thus eliminating the long connecting pipps required in the other types of turbines.

referably each stage is subdivided into a plurality of sections placed side by side and fed in parallel, so as to reduce the diameter of the turbine and keep the centrifugal force within the limits allowed by the material employed, giving at the same time a vmore compact machine. Preferably the low-pressure stage comprises a number of sections which is a multiple of the number of sections of the high-pressure sta e and the arrangement of the sections is suc as to deliver the pressure fluid without any considerable loss in flowingl from one stage to the next. "In the caseV of higher power turbines, according to this invention a middlepressure stage 1s used comprising one or a plurality of sections which are conveniently placed between the high-pressure stages so as' not to increase in the least' the outer diameter of the turbine. l,

By the peculiar arrangement and subdivision of the stages it is possible to obtain the rotor blade carriers as members of easy manufacture that are connected together by successive axial struction exceptionally cheap. i Y Y A further important feature of this invention consists in that the distribution of the stages allows a perfect automatic bal- Y iently chosen points rotating members to be obas of arranging in convencompensating chambers, when it is necessary to eliminate or reduce the axial thrust exerted by the `pressure fluid in opposite directions on the members of the outer rotor.

When the power of the turbine does not exceed a certainlimit, the inner'and outer ancing of the tained, as well rotors canpbe connected together at one end by'a differential gearing and can be pro- Same name.

fluid directly from the1 `keying making the conas described 1n another application in the e y When, however, the power exceeds an allowable limit with respect to the resistance of. the differential gearing, the two rotors are' maintained inde endent of each other and can be connecte with two consumption machines having the same power and speed features `or inversely 4proportional features, i. e. electric generatingmachines. This latter arrangement shows a characteristic coupling of the shaft of the outside rotor with the shaft of theI con-4 sumption machine, which allows an efficient ventilation of the coupling itself, so as to prevent transmission of heat from the turf-y bine to the consumption machine; of course a similar arrangement vcan be adopted Valso for the shaft of the inner rotor, and in this case the coupling shall be separate and fixed on said shaft owing to obvious assembly grounds.

Further features of my invention shall be set forth in the ap endedspecification Vreferring more specifica ly to the drawings,

wherein: Figure 1 is a longitudinal axial section of the upper half of a reversible turbine with two stages and of middle power;

Figure 2 is a similar section showing a turbine with independent rotors comprislng twostages subdividedy into two and six sections, respectively;`

Figure 3 is-a detailed view thereof and y Figures '4 and 5 show in sectional views similar to those of Figures 1 and 2, res ectively, a reversible turbine and a tur ine with independent rotors comprising three stages subdivided into sections. Referring to Figure 1, 1 denotes the main shaft, on which is keyed the inner rotor consisting shoulder 3 of the shaftl and of the vrotor blade carrier comprising a centralp'art 4 for high pressure, an intermediate connecting part 5 provided with holes 6 for the flow of the pressure Huid and a peripheral portion adapted to carry the blades of one of the sections of the low-pressure sta e, which, in the example lshown is subdivi ed,A into two sections B1 and B2, respectively. The rotor blade carrier of the other section B2 consists of an annular disc mounted in a hot condiprojections 9 of the porportion forms together with the rotor lade carrier'4 a balancing chamber divided by a labyrinth 16 into a lower compartment 17 communicating through holes 18 directly with the admission pipe 19 for the pressure fiuid and an upper compartment 20 com`' municating with the exhaust chamber of the high-pressure stage and at the same time with the admission chamber for the lowpressure stage.

Rods ,21 placed at regular intervals on the periphery of the pieces 13 and 14 connect in due spaced relation the lateral carriers 11 and 15 and the central ring 22 fixed to the -ends of the circular series of outer blades 23 of the sections B1 and Biz. Said rods, preferably of rhomboid section extend through holes on the periphery of the por tions 13 and 14`of the ring 22 and said portions are maintained exactly spaced by a tenon and notch and lock key connection between them and the rods; for this purpose these latter are provided with notches 24 engaging the edges of the holes through which the rods extend, said rods being held in dposition by keys- 25 inserted between the ro s and the opposite hole wall.

The sleeve l0 carries a circular series of openings 2G establishing communication between the admission pipe 19 and the connecting pipe 27 fast Wlth the stationary casing 28 of the turbine. Labyrinth ackings are arranged in suitable points o the machine, e.. g. the packings 29-30 and 31 between the stationary part and the outside rotor and the packings 32 between the hub of the inner rotor and the sleeve-shaft 10 of the outside rotor.

The turbine is of the reversible ty e, the rotors are therefore connected togetlier at one end in the known` manner by means of the differential gearingv 33 (of which the drawing only show s a sector) and carry at their other end the fixed members 34 and 35, respectively-,lof a dog clutch, the slidable element whereof is fast in rotation with the propeller shaft 37.

Figure 2 shows a turbine with two stages, wherein the high-pressure stage is subdivided into two parallel sections and the low-pressure stage is subdivided into six parallel sections concentrical to the former. Owing to the high power of this turbine the rotors are made independent and in this case the turbine is adapted to drive two opto carry erating machines having the same power and s eed features. The connection between the s aft 40 of the outside rotor 'and the shaft 41 of the operating machine (not illustrated)` is effected by means of a special coupling shown in detail in Figure 3. This joint comprises two cups 42 integral or secured in any suitable way to the shafts 40, 4l 4and provided with connecting flanges 43.y The cups prevent the transmission of heat from the turbine to the operating machine and for this purpose they are formed on their walls with holes 44 conveniently inclined with respect to the axis of the shaft so as to generate by the rotation of this latter a strong circulation of air within the cu s.

'I ihe inner rotor of this turbine comprisesl for the sections A1 and A2' of the l1igh-pres sure stage a couple of central rotor blade carriers 45 placed in contact with each other with the interposition of suitable packing rings 46 lodged in circular grooves formed on the contacting surfaces. Cylindrical bodies or drums 47 extend from the edge of these carriers to the outside concentrically to the turbine axis, and at the ends of said drums 47 are situated the rotor blade carriers of the sections, B1, B2 and B5, B,i of the low-pressure stage. Each of these rotor blade carriers consists of an element 48 fast with the drum 47 and of an annular element 49 which is mounted in a hot'condition on annular projections50 of the member 48. A slightly different arrangement is provided in the central part, wherein the'rotor blade carrier of the stages E34-B, comprises elements 51 and 52 connected together in a hot condition similarly to the elements 48 and 49 and directly lodged on the ring' 53 of the central carriers. For element 52 is formed with an annularrib 54 which fits between the carriers 45 and engages a plurality of pins 55 that hold it against rotation'. The longitudinal section of the inner rotor thus formed has the characteristic shape of a Candlestick with three arms.

The outside rotor comprises the rotor blade carriers 55, 55 of the sections A, and A2- of .the high-pressure stage, the cylindrical Ybodies 56-56 extending tothe outside from the edge of said carriers and the rotor blade carriers 57--57 of the end sections :B1-B2 of the low-pressure stage. The rotor blade carriers 57-57' are connected together by means of rods 58 regularly spaced on the periphery and supporting the rings 59 surrounding the rotor blade carriers of the low-pressure stage of the inner rotor and the rotor'blade carriers of the stages Bz---B3 and l134-43..; consisting oftwo elements conneclt'ed. together in the manner already set fort 1. e

Between the turbine casing 6() and the fixing purposes the erally by rods 81 sup rotor blade carriers. of the highressure stage are provided compensating c ambers 61 as described with reference to -Fi re 1.

lln this case, however, -in order to" ave a prompt balance when starting the turbines, said compensating chambers are reduced in volume Aby lacing therein filling rings v62 secured to t e casing. A

As in the foregoing construction labyrinth packings 63 are placed in the points 1nrelative motion along the path of the pressure fluid in order to ensure a tight )oint and the rotor blade carriers are formed with connecting holes 64 so that the pressure iiuid may low easily to the various sections of the high-pressure and low-pressure stages and to the balancing chambers.

The same principles iollowed in the constructions of two-stage turbines illustrated in Figures 1 to 3 are employed in connection with three-stage turbines. Figure 4 shows in longitudinal axial section a reversible three-stage turbine, wherein the inner rotor comprises a coupleof central carriers 70, of

which the hubs 71 are directly keyed on the main shaft ,72. ,The said carriers are arrangd in Contact with each other and carry on t eir outer faces the blades of the sections Ml--M2 of the intermediate pressure stage. In the central portion of the carriers 'are provided the tubular bodies 73 ending with the rotor blade carriers 74 for the sections A1 and A2 of the high-pressure stage and provided with hubs 75 tightly surrounding the hubs 71 of the carriers 70. Frustrumshaped bodies 75 extend laterally from the periphery of the carriers 70 and carry on their base in the manner of flanges the `rotor blade carriers 77 for the blades of the sec-V tions Bl---B2 and 13a-B4, respectively, of

the low-pressure stage. These carriers com# lprise two elements connected together by eying in a hot state and forming a hollow triangular section as described with referCh ence to Figures 1 and 2.

The outside rotor comprises the carriers 79 and 78 of the sections A1L and A2 of the high-pressure stage, to the edges whereof are secured the tubular flared bodies 80 carrying in their annular central portion the blades of the sections Ml--M2 of the .intermediate-pressure stage and in the peripheral portion of the blades of the sections B, and B4 of the low-pressure stage. The tubular bodies 80 are connected together periphrting the carrier 82 carrying the blades o the low-pressure sections Bz-B, and the rings 83 surrounding the carriers 77. As in the construction according to Figure 1, the .shaft 72 is connected .at one end with the sleeve 84 fast with the rotor blade carrier 78 through the differential gearing 85 shown parta ly ,in the drawing. At its op osite means of the clutch 86 e shaft 72 or the the sections A1 and A2 of the high-pressure stage; whence it flows back towards the axis between 'the rotor blade carriers 74 and 80,

and passes through the sections`M1---M, of the intermediate-pressure stage by which it is directly supplied to the four sections of 89, and flows into the longithe low-pressure sta e. In this case the Y rotor blade carriers o each stage are inter-4 balanced and the balancingv chambers are thus dispensed with.

Figure 5 shows a very high-power turbine including three stages, wherein the highpressure stage comprlses two sections Al--Az supplied through independent lateral feed pipes 100,'the middle-pressure stage comprises four sections M1. M2, M3 and M4 arranged between the sections A1 and Azand the low-'pressure stagg. comprises eight-sections Bl, B2 s arranged concentrically around the middle-pressure .and highpressure stages. To the shaft 101 is keyed the inner rotor comprising the rotor blade carriers 102, 102 and 103, 103 cou led two by two and carrying the blades of t e inter mediate pressure sections M1 M2 and Ms M4, respectively. Y The rotor blade carriers 102 and 102 extend radially with the inter sition of thin flanges 106 so as to form tu ular bodies 104:-104 carrying at theirends the rotor sections Bl B2 and B1 13 respectively, of the low-pressure stage. Similarly with the interposition of a thin ange 1 and carry the annular rotor blade carriers 108-108 of the sections Bs B, and Bts B, of the low-pressure stage. Laterally of the pairs of carriers 102-103 and 102-103 are keyed to the shaft 101 the rotor blade carriers 109, 109v of the sections A, A, of the high-pressure stage. The outside rotor comprises the rotor b ade carriers 110-110 of the high-pressure sections A, A, and their relative sleeve-shafts 111-111., the conical tubular bodies 112-112 connected to the rotor blade carriers 110.-;110 'by thin flanges 113 and carrying internally the rotor blade carriers 114--114 of the sections Ml M4 of the middle-pressure stage and externally the rotor blade carriers 11'5-115 of the lowpressure sections B, and Bs.

The rotor blade carriers 115--115Y are blade .carriers 105--105 of the the rotorl `blade carriers 103 and 103 extend radialy ros the rotor blade carriers 118-118' of the sections B2 B3 and B6 B., and the rings 119-119 surrounding the rotor blade carriers 105--105.

The rotor blade carrier 117 divides the turbine into two symmetrical parts separately traversed by two streams of pressure fluid that is discharged into a common casing`120.

he thin flanges provided in the intermediate zones between the high-pressure elements and the low-pressure elements have the ver im ortant object to make the parts self-adJusta le under the action of the centrifugal force by their flexibility. The restrained section of these flanges offers moreover an efiicient resistance to the transmission of heat. y

It is obvious that such zones of restrained section or zones of flexibility are provided in all those points where they are required by particular working and temperature conditions; examples of such zones of flexibility are also shown by 121 in Fig. 1.

It will be understood from what has been described above that the examples illustrated are all based on the same principle of dividing the stages into a plurality ofsections placed side by side according to the turbine power and of arranging and generally forming the said sections in a similar manner in the various types of turbines; while leaving this principle unaltered the said turbines can be modified without departing from the spirit of this invention as set forth in the appended claims.

What I claim is:

l. In a'radial turbine a main shaft, an inner rotor mounted on said main shaft and comprising a rotor blade carrier having a central seriesof blades for the high-pressure stage on one face and a peri heral series of blades concentrical to the ormer on each face for the low-pressure stage, the series of blades for the low-pressure stage being divided from, the series of-blades of the highpressure stage by an intermediate portion of the rotor blade carrier provided with openings and a-thin annular liexible flange, a hollow shaft mounted concentrically around the main shaft, an outside rotor keyed on said hollow shaft and comprising a couple o'f rotor blade carriers placed laterally of the rotor blade carrier of the inner rotor, a central series of blades mounted on one face of one of said rotor blade Carriers for co-operating with the central series of blades of the inner rotor, a peripheral series of blades on a face of each of said rotor blade carriers for co-operating with the peripheral series of blades of the inner rotor and an intermediate portion ofthe rotor blade carrier between the series of blades of the highpressure and lowressure stages having a thin annular fleXib e flange.

In a radial turbine, a casing, a main shaft, an inner rotor mounted on said shaft and comprising a rotor blade carrier having a central series of blades for the high-pressure stage on one face and a peri heral series of blades concentrical to the former on each face for the low-pressure stage, an intermediate portion of the rotor blade carrier between the high-pressure and low-pressure stage, said portion being of restrained section in order to be flexible, a hollow shaft mounted concentrically around the main shaft, an outside rotor keyed on said hollow shaft and comprising rotor blade carriers arranged laterally of the rotor blade carrier of the inner rotor, a central series of blades mounted on a face of each of saidrotor blade carriers for co-operating with the blades of the high-pressure stage of the inner rotor, a peripheral series of blades on a face of each of said rotor blade carriers for co-operating with the blades of the low-pressure stage of the inner rotor, an intermediate portion of one of the outer rotor blade carriers between the high-pressure and low-pressure stages, said portion beingof restrained section in order to be flexible, and a compensating chamber between the other outer rotor blade carrier and the inner rotor blade carrier, said chamber communicating with the fluid admission aimliance and being separated by a labyrinth packing from the exhaust of the high-pressure stage.

3. In a radial turbine, an inner rotor comprising disk-shaped members having a central series of blades for the high-pressure stage and a peripheral series of blades concentrical to the former for the low-pressure stage, an outer rotor comprising disk-shaped members having series of blades co-operating with the series of blades of the high-pressure and low-pressure stages of the inner rotor, the rotor blade carriers of the inner rotor and the rotor blade carriers of the outer rotor being connected together by axial keying.

4. In .a radial turbine, a main shaft, an inner rotor mounted on said shaft and comprising rotor blade carriers having a central series of blades for the high-pressure stage and atperipheral series of blades concentrical to the former for the low-pressure stage,

an outside rotor mounted on said hollow shaft and comprising rotor blade carriers having series of blades co-operating with the series of blades of the high-pressure and low-pressure stages of the inner rotor, a differential mechanism at one end for con necting the hollow shaft with the main shaft, a driven shaft at the other end and a clutch mechanism for selectively connecting said driven shaft with the main shaft and hollow shaft.

5. In a radial turbine a main shaft, an inner rotor mounted on said shaft and comprising disk-shaped rotor blade carriers hav -a hollow shaft surrounding the main shaft,

ing a central series of blades for the highpressure stage and a peripheral series of blades concentrical to, the ormer for the low-pressure stage, a hollow shaft mounted concentrically to and turning independently of the main shaft, an outside rotor mounted on said hollow shaft and comprising disksha ed rotor blade carriers having series of bla es co-operating with the series of blades of the high-pressure and low-pressure sta es of said inner rotor, a driven shaft an a coupling device between said driven shaft and one of said rotor shafts.

6. In a radial turbine a casing, an inner rotor comprising disk-shaped rotor blade carriers having a central series of blades for the highressure stage and a eri heral series of lades concentrical to t e ormer for the lowressure stage, an outside rotor comprising isk-shaped rotor blade carriers having series of blades co-operating with the series of blades of the high-pressure and lowpressure sta es of the inner rotor, compensating chain rs between the end carriers of the outer rotor and the casing, openings for establishin communication between said chambers and e admission pipe of the pressure fluid, and labyrinth packing separating saidl chambers from the exhaust chamber oi'4 the turbine.

7. In a radial turbine a casing, an inner rotor m comprising disk-shaped rotor blade carriers having a central series of blades for the highressure stage and a eri heral series of lades concentrical to t e ormer for the low-(pressure stage, an outside ,rotor comprising 'sk-sha ed rotor blade carriers having series of bl es cooperating with the series of blades of the high-pressure and low-pressure stages of the inner rotor, compensating chambers between the end carriers of the outer rotor and the casing), openings for establishing communication e said chambers and the admission pipe of the ressure fluid, lab 'nth packings separating said chambers rom the exhaust chamber of the turbine and filling rings adapted to reduce the volume of said chambers in order to obtain an instantaneous action of said compensating chambers when starting the turbine.

8. In a radial turbine, an inner rotor comrisingdisk-shaped rotor blade carriers subivided at their peri hery into a plurality 'of annular parallel anges, a central series of blades on each of said carriers forming an element of a section of the high-pressure stage, a series of blades mounted on both faces of the peri heral flanges and forming the elements of t e sections of the low-pressure stage, an outside rotor comprising a couple of end carriers, each carryin a cenr tral series of blades forming the ot er element of the section of the high-pressure stage and a peripheral series of blades formof the end sections of the low-pressure stage, annular intermediate rotor blade carriers carrying the series of blades forming the other element of the intermediate sections of the low-pressure stage and means for rigidl connecting together the end carriers and t e annular intermediate carriers inv adjusted position.

9.. In a radial turbine, an inner rotor comprising disk-,shaped rotor blade carriers subdivided at their peri 'her-y into a plurality of annulaiparallel liinges, a central series of blades on each of said carriers lforming an element of a section of the high-pressure stage, a series o blades mounted on both faces of the peri heral flanges and forming the elements of t e sections of the low-pressure stage, an outside rotor comprising a couple of end carriers, each carryin a central series of blades forming the ot er element of the sections of the hi h-pressure stageand a peripheral series of blades forming the other element of the end sections of the 10W-pressure stage, annular intermediate rotor blade carriersV carrying the series of blades forming the other element of the intermediate sections of the low-pressure stage and a plurality of rods regularly spaced on the eriphery of-said end carriers for connecting together these latter and supporting and holding in position said annularintermediate carriers.

ing the other element leo 10. I n a radial turbine, an inner rotor comprisin disk-shapedrotor blade carriers subdivide at their ri hery into .a plurality of annular para el an a central series of blades on e'ach of said carriers forming an element of a section of the highressure stage, a series of blades moun on both faces of the peripheral anges and forming the elements of the sections ofthe low-pressure stage, an outside rotor comrising a couple of end carriers, each carryin a central series of blades formingl t e ot er element of the sections of the ighpressure stage and a peripheral series of' blades forming the other element of the end sections of the low-pressure stage, annular intermediate rotor blade carriers carrying the series of blades forming the other element of the intermediate sections ofr the rings closely surrounding the elements of the sections ofthe lowressure stage of the inner rotor and means or rigidly connecting together the end carriers, the annular carriers and the intermediate rings.

11. In a radial turbine, A an inner rotor comprising disk-shaped rotor blade carriers subdivided at their l-periphery into a plurality of annular para el anges, a cenlow-pressure stage,

forming an element of a section of the highressure stage alseries of blades mounted on th faces .of the peripheral iianges and tral series of blades on each of said carriers the low-pressure stage, annular-intermedi-- ate rotor blade carriers carrying the series of blades forming the other element of the intermediate sections of the low-pressure stage, rings closely surrounding theelements of the sections of the lowressure stage of the inner rotor and rods o rhomboid section for rigidly connecting together sald end carriers and supporting and holding in position said annular rotor blade carriers and said intermediate rings, these latter being connected to said rods by a tenon and notch and lock key connection.

12. In a radial turbine the combination with'a high-pressure stage divided into sec tions placed side by side, of a middle-pressure stage divided into sections placed between the sections of the high-pressure sections and of a lowressure section comprlsing la plurality ofp sections arranged concentrically around the high-pressure and middle-pressure stages, the space between the low-pressure sections and the high-pressure and middle-pressure sections forming the exhaust chamber for the middle-pressure stage and the supply chamber for the lowpressure stage. v

13. In a radial turbine an inner rotor comprising a couple of end rotor blade carriers each carrying a series of blades forming an element of a section of the high-pressure stage, a disk-shaped rotor blade carrier subdivided at its periphery into a plurality of annular parallel flanges, central series of blades mounted on both faces of said carrier and formin blades mounted on both faces of the peripheral flanges and forming the elements of the Vsections of the low-pressure stage, an outside rotor comprising a couple of end rotor blade carriers, an annular rotor blade carrier fixed to each of said carriers and having an expansion extending inwardly between the rotor blade carriers of the highpressure and middle-pressure sections of the inner rotor, a central series of blades carried by each of said end carriers and forml ing the. other element of the sections of the the elements of the sec-V tions'of the mid le-pressure stage, series of termediate sections of the low-pressure stage and means for rigidly connecting together the end carriers and the annular intermediate carriers -in adjusted position.

` 14. In a radial turbine a central shaft, an inner rotor comprising a couple of end carriers each carrylng a series of blades forming an element of a section of the high-pressure stage, a disk-shaped rotor blade carrier subdivided at its peripheryr into a plurality of annular parallel flanges, central series of blades mounted on both faces of said carrier and forming the elements of the sections of the middle-pressure stage, series of blades mounted on both faces of the peripheral flanges and forming the elements of the,sec tions of the low-pressure stage, a hollow shaft surrounding the main shaft, lan outside rotor comprising'a couple of end rotor blade carriers, an annular rotor blade carrier fixed to each of said carriers and having an expansion extending inwardly between the rotor blade carriers of the high-pressure and middle-pressure sections of -the inner rotor, a central series of blades carried by each of said end carriers and forming the other 'element of the sections of the highpressure stage, a series of blades carried by said expansions extending inwardly and forming the other element of the middlepressure sections, a peripheral series of blades carried by each end carrier forming the vother element of the end sections of the low-pressure stage, a diierential gearing at one end for connecting the hollow shaft with with the` main shaft, a driven shaftat the other end and a clutch for selectively connecting said .driven shaft with the main shaft and with the hollow shaft.

15. In a radial turbine, a main shaft, an inner rotor comprising a couple of end rotor blade carriers each carrying a series' of blades forming an element of a sectionA of the high-pressure stage,l a disk-shaped rotor blade carrier subdivlded vat its periphery into a plurality of annular parallel flanges, central series of blades mounted on both faces of said carrier and forming the elements of the sections of the middle-pressure stage, series of blades mounted on both faces of the peripheral flanges and forming the elements of the sections of the low-pressure stage, a hollow shaft mounted concentrically to and turning independently of the main shaft, an outside rotor comprising a couple of end rotor blade carriers, an annular rotor blade carrier fixed to each of Y said carriers and having an expansion extending inwardl betweenl the rotor blade carriers of the high-pressure and middlepressure sectionsk of the inner rotor, a central series of blades carried by each of said end carriers and forming the other element -of the sections of the high-pressure stage,

a series of blades carried by said expansions extending inwardly and forming the other element of the sections of the middle-pres sure st a e and peri heral series of blades carrier forming-,the

carried y each en other element of the end sections of the lowressure stage, a driven shaft and a cou ling evice between said driven shaft an of the rotor shafts in. the form of flanged cups connected together to form a chamber, said cups being provided'with holes inclined to the axis of rotation in order to improve the circulation of air in said cham ber during rotation.

I6. In a radial turbine, an inner rotor.

comprising a couple of end rotor blade carriers each carrying a series of blades forming an element of a section of the high-presrier vand forming the elements of the seca sure sta e, a disk-sha d rotor Ablade carrier subdivi ed at its perlpheryinto a plurality of annular parallel flanges, central series of blades mounted on both faces of said -carone. lto ether these latter andwsuppo y rotors comprising disk sha eral flanges and forming the elements of the sections of the lowressure se and aplurality of rods regu ly spa onthe periphery of said end carriers for connectm rting an ho ding in position the annular intermediate carrlers. 4

17. In a radial turbine, inner and outer 'i having a central series of b adesfor the hi h ressure stage,i a peripheral series of bla es or the low pressure s fand an intermediate connecting portion aving an-annular restricted vzone to provide for the necessary flexibility between the central and peripheral portions. In testimony whereof I have axed my signature.

mann noNoM., y.

members each Y 

